Aircraft spiraling mechanism with jet assistance - E

ABSTRACT

An aircraft in the form of multi-stage missile  1  with a spiral inducing assembly  2  which is capable of inducing the missile to travel in a continuous spiraling motion without the missile rolling. A ramjet  6   b  is attached to a tube  3  that is able to rotate around the encircled part of the fuselage. The ramjet  6   b  is able to rotate in a pivoting manner on the rotate-able tube  3  with respect to the rotate-able tube  3 , thereby changing their pitch relative to the longitudinal axis of the rotate-able tube  3 . Ramjet  6   b  is rotated to a greater than another ramjet on the right side of the tube  3 . The difference in degree of rotation between the ramjets makes the ramjet  6   b  exert a greater force on the rotate-able tube  3  than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube  3  to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube  3 . Thus, as well as forcing the rotate-able tube  3  to rotate, the ramjets would also push the rotate-able tube sideways. But as the rotate-able tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiraling motion of the missile when in flight.

CROSS REFERENCE TO RELATED APPLICATIONS

This is a continuation patent application, being a continuation of theU.S. patent application Ser. No. 11/601,804.

STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT

Not applicable.

REFERENCE TO SEQUENCE LISTING

Not applicable.

BACKGROUND OF THE INVENTION

1. Field of the Invention

This invention is related to the field of aviation dealing with missilesand military attack airplanes.

The aim of this invention is to provide an aircraft that has higherchance of surviving attacks from anti-aircraft weapons. The aircraft canbe in the form a missile or airplane. The aircraft according to thisinvention is fitted with a mechanism that enables the aircraft to travelin a continuous spiraling motion while flying when the mechanism isengaged. The mechanism is such that once activated, the spiraling motionis automatic. The mechanism can also be disengaged by a pilot when sodesired if the aircraft carries a pilot. The spiraling motion isachieved during flight without having to roll the aircraft.

The mechanism could also be fitted to a missile. A spiraling missilewould be more difficult to destroy by lasers, radar controlled machineguns and anti-missile missiles than a missile travelling in a straightline.

2. Description of the Related Art

U.S. Pat. No. 5,322,243 in the name of Stoy shows a missile withvariable pitch fins on a rotate-able tube that are moved by independentactuators, and a computer to control the operation of the actuators.While the intention of Stoy wasn't to provide a missile that couldtravel in a continuous spiraling motion, such a motion could be achievedby the missile shown in Stoy's patent with appropriate programming ofthe controlling computer. The current invention provides a mechanicalmeans for inducing a spiraling motion in an aircraft that does not needa computer to control the position of the fins, jet or rockets on arotate-able tube to induce a spiraling motion in the aircraft.

BRIEF SUMMARY OF THE INVENTION

In this invention the spiraling motion of a fast flying airplane ormissile is achieved by using moveable thrust producing motors on arotate-able tube, with the tube encircling a part of the main body ofthe aircraft and with the tube able to rotate around the encircled partof the aircraft.

The thrust producing motors are attached to the rotate-able tube so thatthey can be rotated in a pivoting manner relative to the rotate-abletube. That is, if the rotate-able tube was kept in a fixed position onthe airplane so as not to rotate, the movement of the thrust producingmotors would resemble the movement of canards on aircraft such as theEurofighter and the recent version of the Sukhoi Su-35. The thrustproducing motors would turn in the same direction. With the thrustproducing motors horizontal, the aircraft or missile would be allowed tofly smoothly. When the thrust producing motors are rotated from thehorizontal position, they would act to pull the airplane or missile intoa spiraling motion.

For the aircraft to enter a spiraling motion, the thrust producingmotors would need to revolve around the body of the aircraft so that theaircraft is pulled in changing directions. In the invention this isachieved by using the rotate-able tube that allows the thrust producingmotors to revolve around the main body of the aircraft—using therotate-able tube as a means of travelling around a part of the main bodyof the aircraft. One motor is rotated more than another motor to createan imbalance between the rotational forces exerted on the rotate-abletube by the motors. The rotation of the rotate-able tube would beautomatic and continuous while the imbalance between the motors wasmaintained. Placing the motors back into a horizontal position wouldremove the imbalance, allowing the rotate-able tube to come to rest.Friction between the aircraft body and rotate-able tube or a brakingmechanism such as a hydraulically activated brake pad being pushedagainst the rotate-able tube could help to stop the rotate-able tubefrom rotating.

Another way of causing the rotate-able tube to rotate is to have motorsof different sizes or different power capabilities, or by unequal fueldeliveries to the motors, such that one motor receives fuel at a greaterrate than another motor.

Although the aircraft could be in the form of a jet propelled airplane,it could be in the form of any one of a range of aircraft such as guidedmissiles and unguided missiles. It could also be in the form ofnon-powered aircraft such as gliders or winged bombs that are designedto glide to a target.

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS

Embodiments of the invention will now be described by way of examplewith reference to the accompanying drawings, of which:

FIG. 1 shows the left side view of a multi-stage missile comprising aspiral inducing assembly.

FIG. 2 shows the left side view of an aircraft in the form of a jetairplane comprising a spiral inducing assembly.

FIG. 3 shows an enlarged view of the spiral inducing assembly of FIG. 2.

FIG. 4 shows the left side of the spiral inducing assembly of FIG. 2after the spiral inducing assembly has been activated to cause aspiraling motion to occur.

FIG. 5 shows the right side of the spiral inducing assembly of FIG. 2.

FIG. 6 shows the spiral inducing assembly of FIG. 2 in an activatedstate, and after the rotate-able tube has been rotated.

FIG. 7 shows an aircraft according to this invention in the form of amissile using the spiral inducing mechanism of FIG. 2

FIG. 8 shows a cross-sectional view of the spiral inducing assembly ofFIG. 2 as viewed from the front of the airplane.

FIG. 9 shows a cross-sectional view of the spiral inducing assembly asviewed from behind the spiral inducing assembly.

FIG. 10 shows the left side of the front of the fuselage of the airplaneof FIG. 2.

FIG. 11 shows how fuel can be delivered to a rotating thrust producingmotor.

FIG. 12 shows how the mechanism could be adapted to fit a multi-stagemissile, for automatic spiraling activation on separation of the finalstage.

FIG. 13 shows a detailed view of how fuel can be forced to flow from afuel container over a prolonged period of time.

DETAILED DESCRIPTION OF THE DRAWINGS

FIG. 1 shows one form of the aircraft 1 as a multi-stage missile 1,fitted with a spiral inducing assembly 2.

Referring to FIG. 1, a rotate-able tube 3 forming part of the spiralinducing assembly 2 can be seen encircling part of the main body 4 ofthe missile 1. The main body has a fore end and aft end. Referring tothis tube 3 as the primary tube 3, the primary tube 3 is able to rotatearound the part of the main body encircled by the primary tube. Theprimary tube is shown as being narrower in the front than at the rear.Also shown is another tube 5 that is fitted to the missile such that itencircles part of the main body 4 of the airplane. Referring to thistube 5 as the activation tube 5, the activation tube 5 is fitted so thatit can be moved in a forward direction relative to the part of the mainbody 4 encircled by the activation tube and then back to its originalposition on the main body. FIG. 1 also shows the edge of one horizontalfin 6 a that is connected to the outside of the primary tube 3. The fin6 a is connected to the outside of primary tube 3 such that it canrotate in a pivoting manner as shown in FIG. 4. A thrust producing meansin the form of a ramjet 6 b is attached to the fin 6 a. Rotation of thefin causes the ramjet to rotate relative to the rotate-able tube.

FIG. 2 shows another form of the aircraft 1 as a jet propelled airplane1, fitted with a spiral inducing assembly 2.

Referring to FIG. 2, a rotate-able tube 3 forming part of the spiralinducing assembly 2 can be seen encircling part of the fuselage 4 of theairplane 1. The fuselage has a fore end and aft end. Referring to thistube 3 as the primary tube 3, the primary tube 3 is able to rotatearound the part of the fuselage encircled by the primary tube. Theprimary tube is shown as being narrower in the front than at the rear.Also shown is another tube 5 that is fitted to the airplane such that itencircles part of the fuselage 4 of the airplane. Referring to this tube5 as the activation tube 5, the activation tube 5 is fitted so that itcan be moved in a forward direction relative to the part of the fuselage4 encircled by the activation tube and then back to its originalposition on the fuselage. FIG. 2 also shows the edge of one horizontalfin 6 a that is connected to the outside of the primary tube 3. The fin6 a is connected to the outside of primary tube 3 such that it canrotate in a pivoting manner as shown in FIG. 4. A ramjet 6 b is attachedto the fin 6 a. Rotation of the fin causes the ramjet to rotate relativeto the rotate-able tube.

FIG. 3 shows an enlarged illustration of the left side of the spiralinducing assembly 2 of FIG. 2. The fin 6 a in FIG. 3 is connected to theoutside of the primary tube 3 by a connecting joint which is in the formof a connecting rod 7. Extended from the connecting rod 7 in FIG. 3 is aprotruding section 8 which is used to rotate the connecting rod 7.Rotation of the connecting rod 7 causes the fin 6 a and ramjet 6 b torotate in a pivoting manner around the connecting rod 7 (in the mannershown in FIG. 4). Linked to the protruding section 8 in FIG. 3 is a stem9. Referring to this stem 9 as an activation stem 9, the activation stem9 is used as a means for pushing the protruding section 8 such that whenthe protruding section 8 is pushed, the protruding section 8 forces theconnecting rod 7 to rotate around the longitudinal axis of theconnecting rod 7. The activation stem 9 is linked to the protrudingsection 8 by a rivet 10. The activation stem 9 is shown as being fittedon the inside of the primary tube 3 and is supported inside the primarytube 3 by a retaining bracket 11. The retaining bracket 11 is rigidlyjoined to the inside of the primary tube but is channeled to allow theactivation stem 9 to move longitudinally between the retaining bracket11 and the primary tube 3. The activation stem 9 is allowed to protruderearward from the primary tube so that it can be reached by theactivation tube 5 when the activation tube 5 is moved forward on thefuselage 4. The activation tube 5 is forced to move forward by anactivation mechanism 12 consisting of hydraulic actuators 13 and 14.

FIG. 4 shows that as the activation tube 5 is forced to move forward onthe fuselage 4 when the hydraulic actuators 13 and 14 extend, iteventually makes contact with the activation stem 9. As the activationtube 5 is forced to move further forward, it pushes the activation stem9 forward on primary tube. As the activation stem 9 is pushed forward,the activation stem pushes against the protruding section 8 and movesthe protruding section 8, thereby rotating the fin 6 a and ramjet 6 baround the connecting rod 7 in a pivoting manner.

In FIG. 4 a rivet 10 is shown connecting the activation stem 9 to theprotruding section 8, which allows movement between the activation stem9 and the protruding section 8. The retaining bracket 11 keeps theactivation stem from moving laterally around the primary tube. Theretaining bracket 11 however does allow longitudinal sliding movement ofthe activation stem 9 so that it can be pushed and moved by theactivation tube 5.

FIG. 5 shows the right side of the spiral inducing assembly 2 of FIG. 2.Shown is another fin 17 a, a ramjet 17 b and another connecting joint inthe form of a connecting rod 18 that connects the fin 17 a to theoutside of the primary tube 3. Another protruding section 19 is used torotate the connecting rod 18, and the activation stem 20 is used to pushthe protruding section 19, with the activation stem 20 linked to theprotruding section 19 by a rivet 21. Also visible in FIG. 5 is theactivation tube 5. The connecting rod 18 allows the fin 17 a and ramjet17 b to rotate in a pivoting manner. Another retaining bracket 22 isshown supporting the respective activation stem 20. FIG. 5 shows thehydraulic actuators 15 and 16 located on the right side of the spiralinducing assembly 2 which also form part of the activation mechanism 12by which the activation tube 5 is forced to move. When the hydraulicactuators 13 14 15 and 16 are forced to extend as hydraulic pressure isapplied to them, they force the activation tube 5 to move forward asshown in FIG. 3. The activation stem 20 in FIG. 4 is shorter than theactivation stem 9 in FIG. 3.

Thus, it can be seen from FIGS. 2, 3, 4 and 5 that the activation tube5, the activation stems 9 and 20, retaining brackets 11 and 22,protruding sections 8 and 19, rivets 10 and 21 used to connect theactivation stems 9 and 20 to respective protruding sections 8 and 19,the connecting joints 7 and 18 in the form of connecting rods 7 and 18,and the activation mechanism 12 used to move the activation tube 5consisting of the hydraulic actuators 13, 14, 15 and 16, collectivelyform a ramjet rotating mechanism, by which ramjet rotating mechanism theramjets can be rotated in the same direction, so that the rotationalforce exerted on the primary tube by one ramjet can be overcome by therotational force exerted on the primary tube by another ramjet.

While ramjets have been shown, other types of jet engines could also beused. Turbojets and turbofans could be used instead of ramjets. Solidfuel or liquid fuel rocket motors could also be used instead of ramjets.If rocket motors are used, they could be rigidly attached to the primarytube, positioned so that thrust could cause the primary tube to rotateand forced in lateral directions. The rocket motors could be of unequalsizes, and or use different fuels or have different rates of fuelsdelivery to achieve rotation of the primary tube.

FIG. 6 shows the spiral inducing assembly of FIG. 2 with the primarytube 3 in a state of rotation. It can be seen comparing FIG. 6 with FIG.2 how the lateral forces on the airplane would be constantly changing,enabling the spiral inducing assembly 2, to force the airplane 1 totravel in a continuous spiraling motion.

FIG. 7 shows an aircraft according to this invention in the form of amissile 1 with a spiral inducing assembly 2 of FIG. 2.

FIG. 8 shows a cross-sectional view of the spiral inducing assembly ofFIG. 2 as viewed from the front of the airplane. Shown here is theprimary tube 3, the fins 6 a and 17 a, the ramjets 6 b and 17 b, thefuselage 4 of the airplane, the activation stems 9 and 20, linked byrivets to the protruding sections 8 and 19 respectively, the connectingrods 7 and 18 penetrating the primary tube 3, and with the protrudingsections 8 and 19 screwed in the connecting rods 7 and 18 respectively.FIG. 8 shows a way of supporting the primary tube 3. Shown is a tube ofsmaller diameter 23 than the primary tube 3. This smaller tube 23 is asupporting tube in that it is used to support the primary tube 3. It hasa smaller diameter than the primary tube 3 to provide a gap 24 betweenthe primary tube 3 and the supporting tube 23. The gap 24 is used toallow freedom of movement to the protruding sections 8 and 19, and theactivation stems 9 and 20 shown positioned inside the primary tube 3.Bolts 25, 26, 27 and 28 are used to join the primary tube 3 to thesupporting tube 23. The supporting tube 23 is able to rotate around theencircled part of the fuselage 4.

FIG. 9 shows a cross-sectional view of the spiral inducing assembly asviewed from behind the spiral inducing assembly. Shown in FIG. 9 are therear ends of the activation stems 9 and 20, and the retaining brackets11 and 22 that support the activation stems 9 and 20, and preventuncontrolled lateral movement of the activation stems 9 and 20.

FIG. 10 shows a side cutting of the part of the fuselage 4 encircled bythe primary tube 3 of FIG. 2. The encircled part of the fuselage 4 canbe seen to be narrower than the rest of the fuselage 4. Thrust bearings29 and 30 are positioned on the narrowed section of fuselage 4. Thethrust bearings are used to prevent the primary tube movinglongitudinally relative to the fuselage 4.

FIG. 11 shows a locking mechanism 31 by which the ramjet 6 b could berestrained in a horizontal position during flight. The locking mechanismis connected to a rigid support 32 on rotate-able tube 3 by a telescopictube 33. The telescopic tube 33 contains a spring 34 to force thelocking mechanism 31 towards the fin 6 a. A stem 35 protruding from thelocking mechanism is used to move the locking mechanism forward when thetube 5 is move forward, thereby allowing the ramjet 6 b to be rotated.FIG. 11 also shows a fuel line 36 for delivering fuel to the ramjet froma flexible fuel container 37 in a cylinder. A piston 38 is used to forcefuel from the fuel container into the fuel line. The piston 38 is forcedto move by a moveable tube 39. The tube 39 is forced to move byhydraulic actuator 40. Hence fuel can be supplied either withrotate-able tube 3 rotating and when it is not rotating. The fuel line36, the fuel container 37 and the piston 38 are attached to therotate-able tube 3. A protruding section 41 prevents the fin 6 a frombeing rotated beyond that protruding section. A spark plug 42 receiveselectrical charge from a battery 43, thereby providing an ignitionsource.

FIG. 12 shows how the spiraling mechanism can be made to work byseparating sections of the multi-stage missile of FIG. 1. The secondarystage comprises the spiraling mechanism, which is connected to theprimary stage 44. When the secondary stage ignites for separation fromthe primary stage, a nylon cord 45 is burnt off, releasing the moveabletube 5 and allowing the springs 46 and 47 to push the moveable tube 5forward on the secondary stage of the missile. The rotate-able tubecould be fitted with a fuel supply system as shown previously, with themovable tube 5 being used to force fuel to flow from a flexible fuelcontainer 48. The fuel container could be made to carry fuel for a jetengine or a chemical that could react with a solid fuel to ignite solidfuel rocket motors.

FIG. 13 shows an enlarged view of the flexible fuel container 48 of FIG.12 and how fuel can be forced to flow from the container 48 over aprolonged period. The container is located within cylinder 49. Fuel isforced to flow from the container when a piston 50 is pushed against thecontainer. The piston 50 is able to move inside a cylinder 51. Thecylinder 51 is forced to move towards the container when the moveabletube 5 of FIG. 11 is moved towards the container. A soft spring 52positioned inside cylinder 51 is able to maintain a force against thepiston 50 over a prolonged period of time, thereby allowing fuel to flowsteadily over a period of time even if the cylinder 51 is pushed so faras to almost enter cylinder 49. Alternatively, a spring could bepositioned inside cylinder 49, between the piston 50 and the container48 or a plug if fuel was kept within cylinder 49 without a container.

1. An aircraft comprising a tube, which tube encircles part of theaircraft and is able to rotate relative to the encircled part of theaircraft, and which tube comprises a plurality of means for producingthrust, with at least one means for producing thrust connected to thetube such that the at least one means for producing thrust is able to berotated in a pivoting manner relative to the tube, and with at least oneadditional means for producing thrust connected to the tube such thatthe at least one additional means for producing thrust is able to berotated in a pivoting manner relative to the tube, and which saidaircraft comprises a means to rotate the at least one means forproducing thrust in a pivoting manner relative to the tube and a meansto rotate the at least one additional means for producing thrust in apivoting manner relative to the tube such that the at least one meansfor producing thrust can be rotated in a pivoting manner relative to thetube in a same direction as a direction of rotation in a pivoting mannerof the at least one additional means for producing thrust relative tothe tube and such that the at least one means for producing thrust isable to be rotated in a pivoting manner to a greater degree than the atleast one additional means for producing thrust, relative to the tube.2. An aircraft comprising a tube, which tube encircles part of theaircraft and is able to rotate relative to the encircled part of theaircraft, and which tube comprises a plurality of means for producingthrust, with at least one means for producing thrust connected to thetube such that the at least one means for producing thrust is able to berotated in a pivoting manner relative to the tube, and with at least oneadditional means for producing thrust connected to the tube such thatthe at least one additional means for producing thrust is able to berotated in a pivoting manner relative to the tube, and which saidaircraft comprises a means to rotate the at least one means forproducing thrust in a pivoting manner relative to the tube and a meansto rotate the at least one additional means for producing thrust in apivoting manner relative to the tube such that the at least one meansfor producing thrust can be rotated in a pivoting manner relative to thetube in a same direction as a direction of rotation in a pivoting mannerof the at least one additional means for producing thrust relative tothe tube and which at least one means for producing thrust, by producingthrust, is able to exert a force on the tube that is greater than aforce that the at least one additional means for producing thrust isable to exert on the tube by producing thrust.
 3. The aircraft of claim1 wherein the means to rotate the at least one means for producingthrust and the means to rotate the at least one additional means forproducing thrust are such that rotation of the at least one means forproducing thrust in a pivoting manner relative to the tube can causerotation of the at least one additional means for producing thrust in apivoting manner relative to the tube in a same direction as a directionof rotation in a pivoting manner of the at least one means for producingthrust relative to the tube.
 4. The aircraft of claim 2 wherein themeans to rotate the at least one means for producing thrust and themeans to rotate the at least one additional means for producing thrustare such that rotation of the at least one means for producing thrust ina pivoting manner relative to the tube can cause rotation of the atleast one additional means for producing thrust in a pivoting mannerrelative to the tube in a same direction as a direction of rotation in apivoting manner of the at least one means for producing thrust relativeto the tube.
 5. The aircraft of claim 1 wherein the said same directionis such that rotation of the at least one means for producing thrust ina pivoting manner relative to the tube is substantially in the samedirection as a direction of rotation of the at least one additionalmeans for producing thrust in a pivoting manner relative to the tube. 6.The aircraft of claim 2 wherein the said same direction is such thatrotation of the at least one means for producing thrust in a pivotingmanner relative to the tube is substantially in the same direction as adirection of rotation of the at least one additional means for producingthrust in a pivoting manner relative to the tube.
 7. The aircraft ofclaim 3 wherein the said same direction is such that rotation of the atleast one means for producing thrust in a pivoting manner relative tothe tube is substantially in the same direction as a direction ofrotation of the at least one additional means for producing thrust in apivoting manner relative to the tube.
 8. The aircraft of claim 4 whereinthe said same direction is such that rotation of the at least one meansfor producing thrust in a pivoting manner relative to the tube issubstantially in the same direction as a direction of rotation of the atleast one additional means for producing thrust in a pivoting mannerrelative to the tube.
 9. The aircraft of claim 1 wherein the saidaircraft is a missile.
 10. The aircraft of claim 2 wherein the saidaircraft is a missile.
 11. The aircraft of claim 3 wherein the saidaircraft is a missile.
 12. The aircraft of claim 4 wherein the saidaircraft is a missile.
 13. The aircraft of claim 5 wherein the saidaircraft is a missile.
 14. The aircraft of claim 6 wherein the saidaircraft is a missile.
 15. The aircraft of claim 7 wherein the saidaircraft is a missile.
 16. The aircraft of claim 8 wherein the saidaircraft is a missile.
 17. An aircraft comprising a tube, which tubeencircles part of the aircraft and is able to rotate relative to theencircled part of the aircraft, and which tube comprises at least onemeans for producing thrust, which said at least one means for producingthrust is able to produce thrust in a direction such that a force couldbe exerted on the tube by the at least one means for producing thrust,and which force is such that the tube could be forced to rotate in onedirection relative to the encircled part of the aircraft, and the tubecomprises at least one additional means for producing thrust, which atleast one additional means for producing thrust is able to producethrust in a direction such that as a result of the thrust produced bythe at least one additional means for producing thrust another forcecould be exerted on the tube by the at least one additional means forproducing thrust, which another force is such that the tube could beforced to rotate in a direction that is opposite to the said onedirection if no other force acted on the tube, and which force exertedon the tube by the at least one means for producing thrust is greaterthan the another force exerted on the tube by the at least oneadditional means for producing thrust.
 18. The aircraft of claim 17wherein the said aircraft is a missile.